|Publication number||US7014359 B2|
|Application number||US 10/077,086|
|Publication date||Mar 21, 2006|
|Filing date||Feb 15, 2002|
|Priority date||Mar 13, 2001|
|Also published as||US20020131474|
|Publication number||077086, 10077086, US 7014359 B2, US 7014359B2, US-B2-7014359, US7014359 B2, US7014359B2|
|Original Assignee||Yokogawa Denshikiki Co., Ltd.|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (35), Referenced by (16), Classifications (19), Legal Events (3)|
|External Links: USPTO, USPTO Assignment, Espacenet|
1. Field of the Invention
The present invention relates to a temperature measuring device which is positioned within the airflow flowing into an engine of an aircraft or an external surface of the aircraft, and which measures the temperature of the airflow.
2. Description of the Related Art
Conventionally, on aircraft on which engines are mounted, temperature measuring devices which measure the temperature of airflows are arranged in the air intake or near the intake of the engines, or on an external surface of the aircraft.
The air to the outside of a cruising aircraft forms an airflow at high speed, and it is necessary to measure the total temperature of this airflow. In order to measure the total temperature of the airflow, for example, a temperature measuring device having a structure in which the airflow is guided into a casing having a sensor located inside, a stagnation point in the airflow is formed by the airflow striking the inner surface of the casing and the stagnation temperature at this stagnation point is measured. Alternatively, a temperature measuring device having a structure in which the total temperature is measured by means of restricting the flow rate of the airflow passing through a passage can be used.
In addition, in Japanese Patent Application No. Hei 11-95563 previously filed by the applicant of the present application, a temperature measuring device in which a sensor is provided in the surface of a blade-shaped casing is described. Under practical conditions, this temperature measuring device derives the total temperature by measuring the temperature of the airflow passing over the surface of the casing from the fact that the temperature of the airflow passing over the surface of the casing and causing friction approximates the total temperature at the stagnation point.
However, when an aircraft is cruising in conditions of ice and snow, with the above-mentioned temperature measurement device having a structure in which the airflow strikes the inner wall of the casing, there is the problem that since the ice and snow adhere to and build up inside the casing and on the periphery of the air intake, the air intake becomes blocked, the airflow cannot be guided into the air intake, and it is not possible for the temperature to be measured. In addition, there is the problem that ice and snow adhere to the sensor, accurate temperature measurement is prevented, and the sensor itself becomes damaged. In the same way, the temperature measurement device which has a structure through which the airflow passes also has the problem that the passage becomes blocked by the adhesion of ice and snow, and temperature measurement becomes impossible.
In addition, according to the temperature measurement device described in Japanese Patent Application No. Hei 11-95563, a structure is adopted in which the adhesion and build up of ice and snow on the sensor or in the vicinity of the sensor does not occur. Therefore, problems such as the sensor becoming damaged, or accurate temperature measurement being prevented have been solved. However, when lumps of ice and snow which adhere to the casing become large and detach, these lumps of ice and snow strike the engine. the airframe or equipment of the aircraft, due to the airflow. Therefore, there is the problem that the engine, aircraft or the like will become damaged. It is possible to prevent the icing which causes this type of problem by heating the casing using an electric heater or high temperature engine bleed air, but the structure becomes complex and heavy, and accurate temperature measurement is difficult when the casing is heated.
In light of the above-mentioned problems, the present invention has an object of providing a temperature measuring device which can be used without the provision of a heating mechanism, with which accurate temperature measurement can be carried out, to which ice and snow do not readily adhere, and with which even when ice and snow do adhere, the temperature measuring device itself is not damaged, and the engine or the like are not damaged when the ice and snow detach.
In order to achieve the above-mentioned object, the present invention is a temperature measuring device which comprises an approximately blade-shaped casing arranged within the airflow flowing into an engine of an aircraft or on the exterior surface of an airframe of an aircraft, and which measures the total temperature T1 of an airflow based on the measured temperature T of the airflow flowing over surfaces of the casing, wherein the shape of the casing is set such that lumps of ice and snow which form on a surface of the casing in conditions of ice and snow, and which detach from the casing and are drawn into the engine or onto the airframe or equipment of the aircraft detach at a stage of growth at which they do not cause damage to the engine or the airframe or the equipment of the aircraft.
According to the present invention, even in conditions of ice and snow, since the casing is formed in a shape from which adhered lumps of ice and snow detach without growing to be large, and it is possible to derive the total temperature without the measurement of the stagnation temperature using a structure with which ice and snow accumulate readily, a heating mechanism for the prevention of the adhesion of ice and snow is not necessary, and temperature measurement which is more accurate than conventional devices is possible. In addition, there is no damage to the temperature measuring device due to ice and snow, and furthermore, there is no damage to the engine or to the airframe or the equipment of the aircraft due to the impact of lumps of detached ice and snow. In other words, according to the present invention, it is possible to obtain by means of a simple construction a temperature measuring device with which accurate temperature measurement is possible without damage to the engine, and which does not break readily.
In addition, when the angle of inclination of each blade surface of the casing with respect to the direction of the line of flow of the airflow is specified so that lumps of ice and snow detach at a stage of growth at which they do not cause damage to the engine or the airframe or the equipment of the aircraft, it is difficult for the lumps of ice and snow to become adhered to the leading edge and grow rearward. In addition, since the surface area for adhesion on the casing is small, adhesive strength for the casing is weak. Consequently, the growth of ice and snow can be controlled, it is possible for the ice and snow to detach readily, and therefore, it is possible to obtain a temperature measuring device which more reliably does not cause damage to the engine.
In addition, when the width of the leading edge of the casing with respect to the direction of the line of flow of the airflow is specified so that lumps of ice and snow detach at a stage of growth at which they do not cause damage to the engine or the airframe or the equipment of the aircraft, the surface area of the casing to which lumps of ice and snow can adhere is small, and the shearing strength of the adhered section is weak, therefore, they break easily, and lumps of ice and snow do not adhere strongly to the casing. Consequently, it is possible to control the growth of ice and snow, and for the ice and snow to detach readily, therefore, it is possible to obtain a temperature measuring device which more reliably does not cause damage to the engine.
In addition, when the angle of inclination of the leading edge of the casing with respect to the direction of the line of flow of the airflow is specified so that the lumps of ice and snow detach at a stage of growth at which they do not cause damage to the engine or to the airframe or the equipment of the aircraft, the air resistance force exerted on the ice and snow by the airflow causes the ice and snow to detach readily, the ice and snow does not readily adhere to the lower part of the casing, and the adhesive force of the ice and snow does not become strong. Consequently, it is possible to control the growth of the ice and snow, and the ice and snow readily detaches, therefore, it is possible to obtain a temperature measuring device which more reliably does not cause damage to the engine or the like.
In the following, embodiments of the present invention will be explained with reference to the figures.
As shown in
The sensor housing section 22 comprises two airflow traversing surfaces 23 which are arranged so that they are each at an angle of 9° with respect to the line of flow of the airflow and which together form a point angle α of 18°, and an inclined leading edge section 24 formed by a ridge of R 0.1 where these airflow traversing surfaces 23 (blade surfaces) meet, and having an angle of 55° (a sweptback angle β of 35°) with respect to the direction of the line of flow of the airflow when positioned within the airflow. The leading edge section 24 is arranged toward the upstream side within the airflow (to the right in
The temperature sensor 30 uses, for example, a resistance temperature type sensor, a thermocouple, or the like, is provided within the sensor housing section 22 near the surface of the air current traversing surfaces 23, and is connected to electric interface 31 by lead 32. The temperature measured by the temperature sensor 30 is transmitted as an electrical signal via the electric interface 31 to an engine control device (not shown in the figures).
A temperature measuring device 10 having the above-mentioned structure is attached to the top of the inside wall of the airflow guide inlet 41 of the engine 40 using the base 21, and is arranged such that when the aircraft is cruising, the airflow traversing surfaces 23 are in line with the airflow and the leading edge section 24 is toward the upstream side (
Here, the temperature T measured by the present temperature measuring device 10 will be explained.
When the airflow is flowing along the airflow traversing surfaces 23, the air in the vicinity of the surface of the airflow traversing surfaces 23 generates heat due to friction due to the relative speeds of the airflow and the airflow traversing surfaces 23. Therefore, the measured temperature T measured by the temperature sensor 30 is a temperature which has been raised due to the heat from friction.
In addition, in general, the total temperature T1 of air having a static temperature T0 flowing at Mach M is represented by:
T 1 =T 0(1+(κ−1)/2×M 2) (1)
Wherein K is the specific heat ratio of air (≈1.4)
On the other hand, the measured temperature T of an airflow which flows over the surface of the airflow traversing surfaces 23 as in the present invention is, with respect to the static temperature T0, represented by:
T=T 0(1+r(κ−1)/2×M 2) (2)
From Formula (1) and Formula (2), between the total temperature T1 and the measured temperature T, there is a relationship of:
T 1 =T×(1+0.2×M 2)/(1+0.18×M 2)
In other words, there is only a slight difference between the total temperature T1 and the measured temperature T. For example, when M is 0.55, T1=1.006×T, and the difference between them is approximately 0.6%. Consequently, if ę and r are considered to be constant, the measured temperature T and the total temperature T1 become a function of the speed (Mach M) of the airflow. Therefore, it is possible to calculate an accurate total temperature T1 by compensation using this function. Alternatively, it is possible to allow this difference as an error value, and to take the measured temperature T to be the total temperature T1.
Next, the effect of the shape of the casing 20 on the growth and detachment of lumps of ice and snow L which adhere to the temperature measuring device 10 when an aircraft on which engine 40 is mounted is cruising in conditions of ice and snow will be explained.
When an aircraft is cruising in conditions of ice and snow, the airflow at or below the freezing point in which moisture is mixed flows into the air guide intake 41. Therefore, with regard to the temperature measuring device 10, the airflow strikes the leading edge section 24, icing occurs, and lumps of ice and snow L begin to grow (
As shown in
In addition, when the lumps of ice and snow L grow and the force of air resistance becomes greater than the adhesive force (shearing strength) of the lumps of ice and snow L of the iced section, the lumps of ice and snow L of the iced section peel away from the leading edge section 24 (or the vicinity of the iced section breaks up), and the lumps of ice and snow L fall from the leading edge section 24. The lumps of ice and snow L which fall are blown downstream by the airflow and are drawn into the engine 40.
Moreover, as shown in
In addition, as shown in
Estimates were made for the growth and detachment of lumps of ice and snow L for a situation in which this type of temperature measuring device 10 is used. In making these estimates, the shearing strength of a lump of ice and snow L was assumed, and when the shearing stress on a lump of ice and snow L exceeded this shearing strength, the lump of ice and snow L was taken to have detached, and the mass of the lumps of ice and snow L at the time of detaching was calculated. The factors involved in determining the shearing stress are as follows.
Speed, density, total temperature T1 and moisture content of the air
The point angle α
The sweptback angle β
The width a, the height b, and the radius R of the leading edge section 24
The front surface width p; the surface area q of the front surface, the spreading angle r, the thickness s, the adhesion width t, and the adhesion surface area u of a lump of ice and snow L
The intake of a lump of ice and snow L of up to 60 g is permissible for an engine 40 equipped with the present temperature measuring device 10. According to the estimates, the lumps of ice and snow L grow, the shearing stress increases, and the shearing strength is exceeded when the mass of a lump of ice and snow L is 7 g. This is calculated from estimates to be approximately 19 seconds after the icing begins. Additionally, estimated results were obtained showing that after approximately 39 seconds after the start of icing, the shearing stress acting on a lump of ice and snow L would exceed two times the shearing strength, and even if a lump of ice and snow L continued to grow without detaching until this point in time, the mass of the lump of ice and snow L would be approximately 28 g, and this is a mass which is sufficiently permissible if it were drawn into the engine 40. Consequently, by means of the temperature measuring device 10 of the present invention, there will be no damage caused to the engine 40 by detached lumps of ice and snow L.
By means of this temperature measuring device, the following effects can be obtained.
a. Because the sensor housing section 22 is formed so that adhered lumps of ice and snow L do not grow large, no damage will be caused to the engine 40 by lumps of ice and snow L.
b. Since there is no need for a heating mechanism to prevent the adhesion of ice and snow, accurate temperature measurement is possible without the need for an energy source or space for a heating mechanism, and it is possible for the size of the temperature measuring device 10 to be reduced.
c. Since the measured temperature T is at the surface of the airflow traversing surfaces 23 using temperature sensor 30, it is possible to derive the total temperature T1 without the use of a conventionally used stagnation temperature measuring device having a structure on which ice and snow build up easily and with which the temperature measuring device itself maybe damaged
|Cited Patent||Filing date||Publication date||Applicant||Title|
|US3000213 *||Aug 8, 1955||Sep 19, 1961||Cook Electric Co||Fluid testing probe|
|US3348414 *||Oct 9, 1964||Oct 24, 1967||Gen Electric||Gas turbine temperature measuring apparatus|
|US3512414 *||May 23, 1968||May 19, 1970||Rosemount Eng Co Ltd||Slotted airfoil sensor housing|
|US3623368 *||Mar 9, 1970||Nov 30, 1971||Comstock & Wescott||Turbine engine blade pyrometer|
|US4152938||May 19, 1978||May 8, 1979||Karl Danninger||Aircraft temperature probe|
|US4244222 *||Feb 1, 1979||Jan 13, 1981||General Electric Company||Instrumentation probe|
|US4595298 *||May 1, 1985||Jun 17, 1986||The United States Of America As Represented By The Secretary Of The Air Force||Temperature detection system for use on film cooled turbine airfoils|
|US4605315 *||Dec 13, 1984||Aug 12, 1986||United Technologies Corporation||Temperature probe for rotating machinery|
|US4765751 *||Jun 29, 1987||Aug 23, 1988||United Technologies Corporation||Temperature and pressure probe|
|US4902139 *||Apr 13, 1988||Feb 20, 1990||General Electric Company||Apparatus and method for measuring the thermal performance of a heated or cooled component|
|US4916715 *||Apr 13, 1988||Apr 10, 1990||General Electric Company||Method and apparatus for measuring the distribution of heat flux and heat transfer coefficients on the surface of a cooled component used in a high temperature environment|
|US5003295 *||Jul 13, 1989||Mar 26, 1991||Rosemount Inc.||Ice detector probe|
|US5039128 *||Jul 20, 1990||Aug 13, 1991||Romuno Nicholas J||Ski light|
|US5043558 *||Sep 26, 1990||Aug 27, 1991||Weed Instrument Company, Inc.||Deicing apparatus and method utilizing heat distributing means contained within surface channels|
|US5088277 *||Oct 3, 1988||Feb 18, 1992||General Electric Company||Aircraft engine inlet cowl anti-icing system|
|US5226731 *||May 28, 1992||Jul 13, 1993||Electric Power Research Institute||Apparatus for measuring rotor exhaust gas bulk temperature in a combustion turbine and method therefor|
|US5313202 *||Jan 25, 1993||May 17, 1994||Massachusetts Institute Of Technology||Method of and apparatus for detection of ice accretion|
|US5331849||Jul 20, 1992||Jul 26, 1994||Rosemount Inc.||Aerodynamically shaped probe|
|US5438865 *||Dec 16, 1993||Aug 8, 1995||Safe Flight Instrument Corporation||Angle of attack sensor|
|US5678926 *||Dec 9, 1994||Oct 21, 1997||Solartron Group Limited||Thermocouple probe|
|US5731507||May 27, 1994||Mar 24, 1998||Rosemount Aerospace, Inc.||Integral airfoil total temperature sensor|
|US5752674 *||Aug 21, 1996||May 19, 1998||General Electric Company||Sensor ice shield|
|US6109783 *||Aug 21, 1998||Aug 29, 2000||Abb Research Ltd.||Optic pyrometer for gas turbines|
|US6422743 *||Mar 26, 2000||Jul 23, 2002||Allison Advanced Development Company||Method for determining heat transfer performance of an internally cooled structure|
|US6622556 *||Apr 11, 2002||Sep 23, 2003||Spectrasensors, Inc.||Total temperature probe with complimentary sensor cavity|
|US6819265 *||Aug 22, 2002||Nov 16, 2004||Rosemount Aerospace Inc.||Advanced warning ice detection system for aircraft|
|US20020064205 *||Nov 15, 2001||May 30, 2002||Henry Tubbs||Heatable member and temperature monitor therefor|
|US20030155467 *||Feb 11, 2003||Aug 21, 2003||Victor Petrenko||Systems and methods for modifying an ice-to-object interface|
|DE3508787A1 *||Mar 12, 1985||Sep 19, 1985||Waertsilae Oy Ab||Schiff mit rumpf zum einsatz in eisgewaessern|
|EP0835804A2||Aug 8, 1997||Apr 15, 1998||General Electric Company||System for reducing ice mass on an aircraft engine|
|FR2680872A1||Title not available|
|JP2000292267A||Title not available|
|JPH08501623A||Title not available|
|JPH09504102A||Title not available|
|WO2000031508A1||Nov 18, 1999||Jun 2, 2000||Auxitrol S.A.||Improved probe for measuring physical parameters of a fluid flow|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US7150560 *||Sep 7, 2004||Dec 19, 2006||Thales||Device and method for determining total temperature for aircraft|
|US7156552 *||Sep 7, 2004||Jan 2, 2007||University Corporation For Atmospheric Research||Temperature sensor system for mobile platforms|
|US7334939 *||Feb 1, 2005||Feb 26, 2008||Airbus France||Method and device for verifying a temperature value at a destination altitude of an aircraft|
|US8182140 *||Jan 21, 2010||May 22, 2012||Rosemount Aerospace, Inc.||Thermal icing conditions detector|
|US8348501||Jan 8, 2013||Rosemount Aerospace, Inc.||Thermal icing conditions detector|
|US8711008||Aug 20, 2003||Apr 29, 2014||The Boeing Company||Methods and systems for detecting icing conditions|
|US8864370 *||Feb 23, 2011||Oct 21, 2014||Auxitrol S.A.||Ice breaking probe for measuring global air temperature|
|US9079669 *||Jun 30, 2011||Jul 14, 2015||Commercial Aircraft Corporation Of China, Ltd||Icing detector probe and icing detector with the same|
|US20050232332 *||Sep 7, 2004||Oct 20, 2005||Thales||Device and method for determining total temperature for aircraft|
|US20060050767 *||Sep 7, 2004||Mar 9, 2006||Fleming Rex J||Temperature sensor system for mobile platforms|
|US20060056482 *||Feb 1, 2005||Mar 16, 2006||Airbus France||Method and device for verifying a temperature value at a destination altitude of an aircraft|
|US20060219475 *||Mar 30, 2005||Oct 5, 2006||Olsen Ronald F||Flow restrictors for aircraft inlet acoustic treatments, and associated systems and methods|
|US20080218385 *||Aug 20, 2003||Sep 11, 2008||Cook Donald E||Methods and Systems for Detecting Icing Conditions|
|US20100116047 *||Jan 21, 2010||May 13, 2010||Rosemount Aerospace, Inc.||Thermal icing conditions detector|
|US20130022076 *||Feb 23, 2011||Jan 24, 2013||Sebastien Dijon||Ice breaking probe for measuring global air temperature|
|US20130105631 *||Jun 30, 2011||May 2, 2013||Huazhong University Of Science & Technology||Icing detector probe and icing detector with the same|
|U.S. Classification||374/208, 244/134.00R, 244/134.00E, 340/962, 374/E13.006, 374/141, 374/148|
|International Classification||G01M9/06, G01K1/14, F02D35/00, B64D43/00, G01K1/08, B64D15/00, B64C23/00, G01K13/02|
|Cooperative Classification||G01K13/028, G01K13/02|
|European Classification||G01K13/02T, G01K13/02|
|Feb 15, 2002||AS||Assignment|
Owner name: YOKOGAWA DENSHIKIKI CO., LTD., JAPAN
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SUGA, TARO;REEL/FRAME:012611/0392
Effective date: 20020213
|Jul 15, 2009||FPAY||Fee payment|
Year of fee payment: 4
|Jul 29, 2013||FPAY||Fee payment|
Year of fee payment: 8